NATIONAL AERONAUTICAL ESTAFMSHhiEIIl

LlBRARY

C P. No 40 (12,823)

A KC Technical Report

MINISTRY OF SUPPLY

AERONAUTICAL RESEARCH COUNCIL

CURRENT PAPERS

Tests on A.W. Apollo (Brab I I B) in the

N.P.L. Compressed Air Tunnel

C. Salter, MA, C. J W. Miles and P.S. Pusey, B. SC., of the Aerodynamtcs Dwsion. N.P.L

Crown CopyrIght Reserved

LONDON . HIS MAJESTY’S STATIONERY OFFICE

1951

SEVEN ShlLLlNGS NET

C,P. No.40

: *_ Pago 1.

Page3 1;

Pa!ggc 5.

Page 17.

F1g.3.

Corrigenda

SumIn, . Add "Bec~usi: of mechanical failure of the

Modal, lina 5.

dirscrca. See Appendix I.

me Beading Omit "Nortnall'.

Lowr diagrai. "30' Flaps" should read "38' Flaps"

blades in the course of the _tests the results obtained nlth windmilling airscrcns tmro not regnrdcd as being reliable nor thz differences large enough to be significant. X&king use of tho observations however the effect on neutral point does in fact lead to close agreement with the results of full scnlc tests.

Some comparisons with full scale tasts nre appended.

The i;dng section was similar to N&.X 65-2-318 but not quite identical with it.

C.P. N&l+0

Tests onA,W. Apollo (Brb IIB) in the NIP&, Compressed Air Tunnel.

-By- c. salter, &A., C, J, ';I. Miles end P. S. Pusey, B.Sc:~,

of the.Aoro~n~ios Divisicn, N.P.L.

22x-d December, 1949

The report desoribes results of tests on a l/25-~1e model UP to D. Reynolds number of 5 millions, The investigation oovered the effect of clotted flaps, (32' and. 38’), elevators, tail plnne, body-wing fillets and freely rotating airsorewsr

Except for those oases where the flap setting was 32' a general tendency was found for a large decrease in the slope of. the lift curve at an ongla of incidence considerably lower than that corresponding to CL max,

The values found for CL max were disappointingly low and none of the changes of body-wing fillets or alterations of flap shapes or angles led to any appreoiable increase. of 0*3.

ACL max due to flaps WAS of the order

Model

by Messrs. Armstrong Whitworth Air&aft Ltdr to a scale of The wings were made of metal and the body of phenoglaeed wood. An outline drawing with main dimensions is given in Fig. 1.

The wing section NACA 65-2-318 had n maximum thiokness of 18% at O&210 and a IBCU~IIUIU camber of 2124:; at 0.4410~ It was derived from a Coldstein "roof-top" fniring with an NACA camber giving oonstant loading to 0,50 deorensing linearly to sero at the trailing edger It was similar to that previously used for the root on of the Hurricane exoept for a$ p3;ase in the camber in the ratio a value of CL (optimum)

Ordinates for the seotion are based on chord measured to the "&'I trailing edge on A,W, drawing W&T&M, 1308. The aotual trailing edge is a little farther baok and the tail of the seotion therefore slightly 0uspca.

As a result of preliminary work at the R.A.E. and at the N4P.L. a number of body-wing fillets were supplied later for comparative examination, Outline sketches are reproduoed in Fig. 2.

Slotted/

Published by permission of the Director, N a ional Physical Laboratory. t'

-2-

Slotted flaps of ;i@ mean chord and total length equal to 53.776 of the span of the machxne extended across the body and were adjustable for flap nngles of O’, t32O and +38O. Being In three parts the centre

-portion (25.q span) could be retained Ln the sero position so that It was possible to examine, the effect of the out-board sections(27.$ sBan) only. The flaps ore illustrated In Fig. 3,

tlo”, 00, A variety of brackets allowed the elevators to be set in turn at -10' and -20°, and provision was made for flttlng a1rscraw blades

to the freely rotating spinners while the four jet exits were paired off In the usual way.

The normal tnil unit (nt = -1") was detachable and could be replaced either by an alternntive un1.t (nt q +2’) or by a tail falring block without fin or tall plane.

Range of Tests

As the mcan chord of the model was only 0.429 feet a maximum Reynolds number of 5 millions was all that could be obtained but tests were also made at lower values and in p&tlculnr at 0.2 and 0.5 millions for compnrlson with results obtnlned rn Messrs. Armstrong Whitworth’s tunnel and at the R.A.E. respectively.

For a number of reasons including the need to exarmne the influence of the various body-wing fillets the programme had to be somewhat restricted but It is hoped that the information obtain 1s reasonably comprehensive e

The various arrangements considered are llsted in the following table:-

Set

A

B

c

’ D

E

F

G

H

J

x

L

M

N

P

Fillet No. Tail

a

2

10

IO

IO

10

10

10

10

a

10

?lt q -1 O

t,

No Tail

3,

Flaps Elevators (degrees) (degrees)

0 0

32 0

0

32

3?

0

0

38

0

0

0

38

0

38

0

0

0

0 With airscrews

0

0

t10

-10

4 0

Tables/

-3-

Tables and Figures

The appended tables contain the results of various sets of observations rind the figures illustrete the main charnoteristics. In some

. 0ase8 the results were so nearly alike those of one or other of the tables that they q-e omitted; II and F respdotively.

for exauplc sets E and G were closely sinil~r to In the first case the only change was the

replacement of fillet No.8 by No.2 and in the second the attachment of the nlrscrew blades.

Other tests (including set C) of an exploratory or comparative nature are not recorded but are referred to in the text.

Results

Lift coefficient and CL max ourves

A few typical curves of CL against value of R of roughly 3.8 x I 06.

a are given in Fig.4 for a An interesting feature is thnt’with

nearly 011 the variations and adjustments that were examined the slope of the curves decreased considerably at an angle of incidence much earlier than that corresponding to CL mox, (see curves F and H of F1g.4). The points at which the slope fell off could nlways be repejted with good consistency but there was often difficulty in repeating the observations at higher values of a.

The two exceptions to this general tendency occurred with a flop setting of 32” when the model was fitted with body wing fillets Nos. 2 and 8. Curve D in Fig.4 refers to the latter. The curve for the former is closely sir,lllar. In these oases CL ~,IDx was attained at two angles of incidence, one ot the commencement of stalling and the other at a much higher angle. This will be referred to later in the discussion of the effect of flaps.

The variations of cr , max with R are given in Fig.5. The tables include the values of a ot which these maxima oocur.

Pitching Moment and Drag Coefficients ,

Except in the investigation of elevator power no dzfficulty waa experienced in obtaining consistent values of pitching angles of incidence. The curves of Flg.6 illustgate q?$:; ;:;:: conditions at n Reynolds number of about 3.8 x 10 . This value of R has been chosen as giv5ng the best set-of curves for purposes of comparison.

The coefficients are given about a point 0.2j z from the leading edge of the centre wing section and one inch below the body datum (model right way up).

Minimum drag coefficients for the sets of observations where the flaps were set in the zero position are plotted in Fig.7.

Body-Wing Fillets

When first delivered to the N.P.L. the model was fitted with small body-wing fillets No-land as the ,earlier observations showed disappointihgly low maximum lift coefficients at high Reynolds Numbers sdme attention was given to a comparison in this respect of different shapes of fillets (Fig.2).

-lA-

It has already been mentioned that, cn the model with 32’ flap settings, fillets Nosd 2 and 8 showed no difference. Similarly under these conditions there was little to choose between Nos. 8 and 10, while curves B and D in Fig.5 show the similarity as regards Nos. 8 and 9.

At zero flap angles a comparison between curves A and F suggests that fillet No.10 might bc a slight improvement on No.9 at high values of R. A consideration of the shnpe of the 0, against a curves will however show . that the difference is not significant.

In the preliminary mcnsuremcnts made with the small fillet the results were much the sane as those recorded for set A. Generally speaking there is nothing to show that one fill& IS appreciably better than another.

Other Fillets

As a result of a few visual tests at low Reynolds numbers which indicated that flow troubles eught be occurring at the inboard nacelles, the latter were built up with plastxrne fillets, apparently leading to a considerably improvement of the flow. Subsequent measurements of lift did not however show any significant Sain. These ware necessarily made only at moderate values of R because of the inability of plostioine to retain its shape in the high p&sure stream.

Effect of Flaps

In conjunction with other variables the model was examined with flaps at, O", 32' and 38'. Halfway through the experiments the model was returned for modification of the flap brackets to permit a flap angle of 380. At the same time alterations were made to the flap and frize profiles and to the backward travel (Fig.3). Sets A to E, which include all the 32” settings, and also N were onrried out before modification and the remainder which include the 38’ flaps afterwards.

Circumstances did not permit a close investigation into the effect of the alterations but a repeat of set C (outboard portions of flaps at 32', centre portion at 0') with modified 32' flaps showed that the only difference was an increase in the values of a by approximately one degree.

Details of the flaps, frizes and slots are given in the firm's drawings Nos. WTM 1494-6 and 1592 and typical sketches are reproduced in Frg.3. Using the templates employed in construction a check was made of the accuracy of the model in relation to the drawings. The deviations were found to be too small to allow figures to be specified but to illustrate the sort of error found, the 38' flaps were correctly set as regards angle but the backward travel was slightly inadequate while the downward movement was slightly excessive.

A comparison based on actual values of AC& mnx is not entirely satisfactory in view of the large associated values of a for all cases except those mhere the complete flaps (centre and outside portions) ware set at 320. The following tnblt however gives the approximate increases obtained.

Table/

-9-

Comparison .

A&B A&D N & P (No Tail) F&H

' L & M (with Ekindry other

. tests .

Increase

0.3 0.3

Flaps

35 0.55 38' at high Reynolds numbers 0.24 11 II ,I ,I 11 0.26 n 0.33 ,I 38" slightly better than 32'

An examination of the model with only the outboard sections of. flap at 32' resulted in nearly as high a value of maximum lift as with the complete flaps at 32’ but at an angle of incidence of 20' (curve similar to H in Fig.4).

The lift curve D in Fig.4 and the corresponding curves for B, taken in conJunction mth the other evidence, is sufficient to demormtrate that the origirlal arrangement at 32' is the best one. '

It will be noti ed however th t in curve B of Fig.5, the values of CL mx at R = 1.4 x 10 8 and 2.2 x 10 8 are greater than at the top Reynolds numbers. In this region with sets B and D, and as found in sundry other unrecorded observations, all with flaps at 3Z", there was a tendency to double values of CL max.

in Fig.6. The influence of the flaps on pitching moment Cm is indicated

Tazl Plane

Sets F snd A (normal tail), J (alternative tail unit) and N (plain tail fairing) were obtained for the estimation of downwash and tail plane constant a,. Typical pitching mment curves are given in Fig.6.

Elevators

Measurements of pitching mment with elevator settings fl0' showed an unusual variation with change of Reynolds number, thought to be due to the bending of the elevators under load as they could easily be distorted with the fingers. As a check on this, stiffening brackets were attached to the under surface but no mprovement followed and the consistency of repeat observations, usually 'extrerely good in the C.A.T. when conditions are unaltered, was poor. The scatter of points however did not seem to be great enough to justify further investigation. The actunl elevator settings were measured and found ,to be approximtely O', +YO, -, oip 2 *

Elevator power is obtained from sets F, K and L, (unflapped) and H and M (with 38’ flaps).

The effect of freely rotating airscrews was emnined byCa repetition of set F vtith no other mdifioation thon the addition of the blades. The differences were found to be negligible.

Table/

Set A

Plllets No.9 Nonul Tai Flaps at o"

vt = -I0

Elevetors at 0'

P = 1.015 Atms pV2 = 13.22 lb./sq.ft. P ~'2.71 Atmos pV2 = 29.2 lb./sq.ft. v = L.3. FE Rz0.203 xl06 ir = 67.3 m R = 0.493 x 106

-6,l -0.4ja 0.0496 0.1925 -f.6 -0.239 0.0387 o-144 -2.3 -0.425 0.0363 0.1087 -I b0 -o&n 0 0.0353 0.0819 +0.25 +0.104 0.0351 0.q60

1.5 0.27 6 0.0364 0.0317 4.0 0.457 O.@wY -0.0138 6.5 0.705 0.0489 -0.0593 9.05 0.896 0.0699 -0.1037

11.45 1.084 0.0968 -0.1yo 12.7 1.118 0.118 -0.204 14.0 1.118 0.153 -0.217 15.3 1 .oyJ+. 0.197 -0.237 16.65 1.025 0.253 -0.258 19.35 0.723 0.326 -0.204 21.9 0.942 0.389 -0.288 24.5 0.947 0.452 -0.328

c, CD

c, nax 1.12 at 13"

a - 1 cD

-2.35 -0.131 0.02753 0.0799 -1 .@ -0.021 0.0255 0.0777 60.2 +O.lOl o.o2L& 0.05~9 1.45 0.223 0.0250 0.0278 2.7 0.350 0.0275 0.0018 5.2 0.591 0.0371 -o.oQl+ 7.7 0.832 0.0528 -0.0953

10.2 1.04 0.0764 -0.1jyj II 4. 1 .I1 0.0726 -0.1925 12.65 1.155 0.112 -0.208 13.95 I.17 0.141 -0.223 15.25 1.155 0.191 -0.250 16.55 1.12 0.225 -0.272 19.25 1 .oo . 0.281 -0.277

- Y--

CL max 1.17 at 14O

P = 12.63 kttmos pv2 = 135.4 a./~+%. V168.8 n?s R = 2.19 x 406

a

-2.35 -1 .oj +0.2

:-';' . 5.2 7.7

10.2 12.6 13.9 15.2 16.45 17.8 19.1 20.4 21.7 24.3

5. cD

-0.147 0.0229 -0.01 y 0.0216 +o.oyy 0.0199

0.221 0.0212 o-343 0.0237 0.599 0.0337 0.835 0.0497 1 .cr, 0.0738 1.225 0.107 1.30 0.122 1.31 O-i58 1.32 0.202 1.37 0.233 1.395 0.252 1.38 0.301 l-375 0.347 '1.325 0.427

0.1083 0.0815 0.0593 0.0350 o.ooyy

-0.0428 -0.0924 -0.133 -0.1 yy -0.218 b -0.245 I -0.281 -0.307 -0.322 -0.337 -0.360 -0.395

% max 1.39 at 190

Set A (Contd.)/

p = 19.3j i;tms Pv2 = 179.6 Ib./s+ft. v z 63.6 EEi R= 3.18 xl06 ~

a

-2*l+ -0.149 0.0223 0.106 -1 .I -0.025 o.ozog 0.0726 +0.25 +o.ovv 0.0204 o.ojy6

1 .j 0.224 0.0212 0.0349 2.75 0.349 0.0240 0.0096 5.25 0.596 0.03&O -0.0374 7.75 0.833 0.0498 -0.0352

10.25 1.048 0.0717 -0.1324 12.65 I.23 0.103 -0.198 13-85 I .328 0.133 -0.241 15.15 1.267 0.170 -0.Zj7 16.45 I.325 0.203 -0.285 17.8 I.375 0.229 -0.310 19.1 1.41 0.258 -0.326 20.3 1.10 0.300 -0.342 21.7 1.38 o-344 -0.365 23.0 1.355 0.385 -0.3e4 25.65 I.305 0.463 -0.430

I

CD

-0, max 1.41 at 19"

- a

-2.45 +5.35, 11.4 12.55 13-75 15.6 16.3j 37.6 18.85 20.15 21.45 22.8 24.1

-0.140 +0.5yo

1.1L7 1.243 1.254 1.27 1.310 1.375 1 .$O 1.44 1.38 1.335 1.31

!

-%i

/i a Ii

to.1q5 -0.0327 1 -1 .oo -0.1gjo j +0.3 -0.187 j I.55 -0.225 j 2.8 -0.263 -0.282 -0.310 -0.326 -0.145 -0.366 -0.3% -0.4o4

T

-r

c, -0.105 +0.016

0.130 0.233. 0.341 0.582 0.813 1 .a!+ 1.15 1.23 1.22 1.265 1.315 1.35 1.39 1.41 1.37 1.32

-1.23

T T

+-

CD

0.0227 0.0214 0.0212 0.0227 9.0254 a.0355 3.0518 9.0778 o.oaya 3.105 a.128 -3.158 CL193 3.228 3.269 X318

cid

o.og9o 0.0746 0.0526 0.0322 0.0133

-0.0308 -0.0740 -0.1215 -0.1525 -0.1845 -0.218 : -0.260 -4

-0.288 ' -0.310 -0.329 -0.353 -0.370 -0.386

Set B

Fillets No.9 naps at 320

~Jonxd Tail % = -1" Elovntors nt o"

P = 2.78 Atms pV2 = 29.2 lb./s v = 66-l FE3

P = 4.56 hnos pV2 = 49.0 lb./s ft. R = 0.507 x 1 0% v = 67.9 BPS R = 0.845 x 10 %

p = 1.0 ktms pV2 = 13.21 lb.7 q.j v = xc.2 FE3 R = '3.205 x 1 &

-I- / a j Q, r I $1

0.034 0.055 0.027

-0.009 -0.051 -0.089 -0.117 -0.164 -0.238 -0.253 -0.257 -0.268 -0.270 -0.231

-.

a / %I cD % I % . , +o-0657' -0.0515 -0.115 -0.135 -0.189 -0.1925 -0.265 -0.270 I -0.276 ~3

1 I /

/

--

a i

-5.1 0.14s +5.o5 1 .I1

a.8 1.15 10.05 l-535 11.25 1 .!z5 12.5 1.535 13.8 l-525 15.1 1.52 16.4 1-45

(- /

-7

0.0977 0.119 0.102 0.0836 0.113 O-0373 0.124 0.0002 0.141 -o.oL& 0.163 -0.0852 0.180 -0.1127 0.211 -0.180 o-257 .-0.241 0.298 -0.254 0.326 -0.252 0.358 -0.250 0.443 -0.260

I -5.05 / 0.132 -2.5 I 0.368 +o.o5 j 0.599

2.55 / 0.835 5.05 1 I.084 7.6

; I.308 a.85 / I .~2

10.05 11.3

, 1.47 i 1.45

12.6 1 1.425

o-0937 0.0961 0.102 0.116 0.136 O-157 0.175 0.201 0.246 0.288

! I

13.9 / 1.415 ; 0.321

ii:; ; 2;; / gz; .

j *' -"'5...i - I /

I I * I

-5.05 -2.45 +0.05

2.55 5.05

0.117 0.361 0.594 0.823 1 .oao

71.6 l-305 a.85 1.41

IO.05 I.46 11.3 l-445 12.6 1.41 13-Y I 1.41 15.2 . ! 1.435

16.55 / 1 -3' __-L--

I

._-__-----

CL max 1.54 at' IO? CL max 1.47 at IO0 CL ,,,= 1.46 at IO'

c

Set B (Contd.)/

Set B (Contd.)

P = 8.16 htIzxls V = 65.5 FPS

pV* = 81 l 3 Ib./sq.ft . R = 1.w x 106

a,

-5.05 0.152 0.05 0.637

+5*o5 1.12 8r8 lb48

10.0 1 .58 11.25 1.67 12.45 I.755 13.8 1.67 15.05 1.60 j6.35 1.60 17.7 1.59 2or45 I.305

oeoY27 0.101 Oil33 01174 0.189 0.207 0.235 0.283 0.340 0.383 0.423 0.540

-

t

t

CL -I*75 at 12Y'

0 .ovo 0.022

a.053 -0i119 -0.140 -0.164 -0.197 -0.222 -0.284 -0.285 -0.270 -0.246

P = 13.15 Atnns pV2 = 135.5 lb./sq.ft. Vz67.6 ITS R = 2.22 x 106

a

-4.95 0.152 -2.5 0.393 +0.05 0.645

2.55 0.882 5.05 1.115 7.55 l-365

10.0 1.57 11.25 1.675 12.5 1.74 43.75 1.70 15.05 1.69 16.4 1.65 17.75 I-66 20.35 1.64 22.95 1.46

0.0912 0.092 0,101 0.114 0.134

0.191 0.209 0.232 0.310 0.338 0.367 0.403 o-474 O-578

7

I T-

%!

0.0965 0.061 0.0217

-0.0128 -0.0522 -0.1087 -0.140 -0.165 -0.190 -o-j@4 -0.301 -0.291 -0.284 -0.299 -0.286

P = 19.35 xtnos pV2 = 180.0 lb&q.ft. v = 64.2 B = 3.10 x 106

-5.05 -0.1

z5 IO.05 11.3 12.55 13.8 15.1 16.4 17.75 20.35

c, car

0.181 0.089 0.0992 0.642 0.101 010238 1.115 0.132 -Oh0504 1.465 0.175 -0.116 I.575 0.192 -0.140 1.685 0.209 -0.164 1.65 0.258 -0.218 1.63 0.308 -0.288 1.64 0.340 -0.295 1.655 0.367 -0.295 I 1.66 0.395 -0.296 Q 1.66 0.455 -0.300 I

-

cLmx 1.69 at 114~

Set B (C&d.)/

a

P = 21,6 AtmOS pv2 5 230 lb./strft. v = 69.0 FPS R = 3.69 x IO

I CL cD OM

-5.05 -2.5 +0.05

2.6 5.15 7.65

IO*1 11.25 12055 13.8 15.1 1614 17.75 lYbO5 20.25 21.6 22.95

0.189

1.14 1.375 1.59 1.70 1.655 1.645 1.64 I 1 .05 1.65 1 .69 1.70 I ,585 1.50

O&TO 0,094 0,103 0.118

",*;iz 0:193 0.215 0.252 0.311 0.341 Q.372 0.28 0.431

0.1003 odJ574 0,0110

40238 -0.0588 -Or1017 -0.1427 -0.170 -0.215 -0.293 -0.293 -0,296 -0,292 -0.305 -0.311 -0.305 -O.jol

-_--

- IO -

Set B (Contar)

CL- 1.71 at ll+O

Set D/

Set D (E almost identiml)

Fzdlets No.8 Normal Tail q _ -1 map at 320 m&Jrstnt o"

P = 1,00 Xtmos pV2 = 13.25 lb.& v +7416 FPS R = 0.201 x 106

? = 3.00 htmx. pv2 = 29.2 lb./s .ft. r = 63.9 FPS R = 0.517 x IO 2

P = 13.35krm vz66.3 m

pV2=135.81b./s .ft. R=2.31 x 10 %

i+

-5.05 -2.5 +0$5,

::g -7.6

8.85 10.1 11.35 12.6 13.9 15.2 16.5 19.25

T- t T t

% %,I

0.0879 0.0924 0.101 0.116 0.133 0.162 0.179 0.193 0.213 0.255 0.310 0.340 0.368 0.401

*loo9 .06O9 so225

-.0131 -.0518 I s.0922 2 -.I113 , -.I330 -.1563

-0.210 -.289 -,290 -.290 --292

0.477 / -238 0.5aq -.275

-__ T / /

-i-

-I- /

T /

%I a

0.171 0.416 0.662 0.906 1.145 1.38 I.485 1.59 1.685 1.675 1.64 1.645 1~655 1.655 1.63 1.44

0.153 0.0939 0 ‘0845 0,397 0.0971 GO544 0.632 0.0988 0.0272 0.877 0.117 -0.014+ 1.103 0.135 -0.0465 1.345 0.154 -0.0889 1.435 0.178 -0.1147 19495 0.203 -0.166 1.45 0.254 -0.245 I.44 0.298 -0.266 1.465 0.323 -0.265 l-445 0.361 -0.263 1.24 0.469 -0.267

.% cz 0.132 0.361 0.596 0 .a37 1.065 1.30 1.39 Ia42 Id& 1.36 I.365 1.365 1.355 1.16

O-0952 0.113 0:0997 0.091 Or110 0.043 Oil22 -0 .OOl 0.139 -0.03: 0.162 -0.08C Oa181 -0.119 0.218 -0.195 0.262 -0.23: 0.290 -0.236 0.323 -0.23i o-355 -0.239

oh499

.

-0.2;:

-5.l5 -2.55

0 t2.5

::; 8.8

10.0 11.25 12.5 13.8 15.1 17.85

-5.05 .-2.45

to.05 2.55

z5 8185

10.05 11.25 12.5 13.8 15.1 16.4 17.75 20.35 23.05

i

CLmx1.70 at11 o CL - I.50 at IO0

Set D (Contd.)/

- 12 -

Set D (Contd.)

P s 2?& Ltnos pV2 = 229a5 Ib./aq,ft, v = 68.3 FPS R = 3.70 x 10’6

a

-5.05 -2.5 to.05

2.55 5.15

zag5 lo:, Il.3 12.55 13.8 15bl 16.4 17.75 19.0 20.35 23.0

-

--

CL

0.211 0.462 0,703 0.95 1 .I7 1.40 1.50 Is61 1171 1~68 1,615 ;*g5

11675 Ii70 1.685 I.495 c

0, --

0,

o.osye 0.1018 0.0934 0.0680 0.102 0.0183 0,118 -0.0210 0,135 -0.0587 0.160 -0d'TYT 0.174 -0.114 01139 -0,135 0~208 -0.1595 0.256 -0.2135 0.310 -0.287 0.338 -0.291 0,365 -0.2y3 0.398 -0.300 0.430 -0.314 0.468 -0.306 0,569 -0,290

CL max lr72 at II+'

P= 1: v = 75

a

p g&xy 3Tr2 = 13.31 P = 3.22 %mos 2 29.4 lb./sq.ft. &Fes: ~<.::r.;f:y”::

" R = 0.198 x lb./sq.ft./l 136 /j V = 63.15 FPS pV2 R = 0.52 x 106 -

-I-

I -j-

a 4 -T

T

/-

j

l-

-3.2 -1.85 -or6 : +o.65, 3.15* / 5r65 8.1

10.65 II*9 13.2 14.5 15.8 17&5 18.4

+1210 .d.O89

,l;b&j OA'35 C:j62 C.6C2 OS826 0.996 1a55 1 l c7 I.065 I .':8 1.C85 J-93

0.1375 G.107 O.C805 0.0564 Cl .00gci

4 .C j21 -@A838 -0.1755 -0.j95 -2.2% -c .239 -cl .219 -3.278 A.259

-3.2 -1 .y -0.65 +0.6

::15 8.05

1G.6 11.8 13.1 14.4 15.7 17.G 18.j5

-0.226 -0.111 +cI .GGl+

0.123 0.373 0.619 0.842 l&5 1~10 l.G8 1.115 1.13 1 .I1 1.04

0.0312 0.0276 O.C260- 0.0263 0.0301 o,o392 0.0565 O.G616 0.0967 0.127 0.153 0.193 0.256 0.295

0.127 0.4033 GA793 CL551 G.OC46

-@ .a29 -0 .cy& -0.1637 -z.lyI+ -c.2385 a.234 -3.251 -0.284 -C.296

Set 3' (G almost identical)

Fillets No.20 Nom1 Tax1 G = -1 Flaps at O" Electors at O"

0~0378' 0.0361 " OiC37-l 0,04@3' G &.5y c.0575 C&S97 C.112 c.141 G.173 c. .2( 2 t.261 o..m

1

:L ox 1 .o9 at 170 CL-l.13 at Ifi0 * CL - 1.38 at 23'

P=l5.G5 htnos pV2= 137.8 lb./sq.ft. v=63.8 FPs x= 2.30 x 106

a

-3.2 -1 .Y -3.6 +0.55

3.15 5.6 8.1

13.65 13.1 15.65 16.95 18.2 19.5 22.8 22.1 23.4

-0.230 0.0261 -0.113 0.0226 +C.GQ7 0.0211

a.123 O.G2Gl 0.375 0.~246 0.620 ad374 w34.4 0.0527 1.26 Ga0772 1.19 G.1;8 1.255 0.179 1.315 G.2C6 1.355 6.234 1.375 G.268 1.37 1,.3:9 1.345 0.334 1.315 0.383

--

j- Crr

0.:31 0.105 G .OOOl G.0569 O.Gc52

-0.&42 -0.C885 -0.148 1 -0.2S5 G -0.263 I -G.287 -0.3lC -0.329 -L&4 -2.359 -2.380

Set F (C&d.)/

Set F (coda.)

P = 24.1 ktnos pv2 = 216 lb./s v = 63.6 FFS R = 3.73 x 10 2

.ft. P = 24.7 btms pV2 = V = 8$.4 FFS

366 lb./sg.ft. R = 4.96 x 10

a

-3.15 -01227 0.0243 -1.85 -0.108 0.0212 -0.6 +o.GOY O&201 +S.65 0.128 0.02c2

3.15 0,375 C.0249 5.6 O&O 0.0368 8.1 C.847 0.0534

lCi6 1 A7 0.0755 13.1 1.21 0.1175 15.65 1.27 c.177 16.9 4.33 G.264 13.2 1.365 0.233 19.5 1.42 17.259 23.8 1.42 0,296 22.15 1.375 0.343 23.4 1.35 Cl.386

CL -1.43 at 2o"

0.124 0~0990 0.0753 0.0517 C.CO22

-D.C433 -C.O856 4.131 -0.2C4 -0.262 --.285 -3.313 -C.336 a.353 d.373 -0.393

a A-

-3.25 -1.95 -0.6 +0.7

;::5 8.15

IS.65 13.1 14.35 15.65 16.9 18.2 19.4 20.7 22.C5 23.3

-0.2:5 -0.090 +O.Cjl

0.146 C.38C 0.626 d.866 1 .;yi 1.222 1.237 1.319 1.353 1 .4Ll3 1.445 I .46s 1.4;7 1.361

-

i

-7

O.C256 0.0219 O.Z198 0.019y 0. C245 O&336 OA515 CA743 c.117 ~~.I51 0.177 0.2C5 0.234 6.263 G.293 0.344 CJ.js5

0.119 O&v26 0.0694 GA476 O.CO64

-L&366 -C&832 -c.134 -5.2c5 4 -239 X.274 -0.294 -C.326 4 .ytv -c.364 A.383 -G.4;3

1 -

P = 1.0 Ltms pV* = 13.3 lb./s .ft. v = 75.7 FE-i R = 0.198 x 10 %

a

:z5 *I*75

g5

7195 Ya2

WC.5 11.75 13.05 14.35

-7 0.233 0.463 0.684 0092 lb16 lo24 1.33 1.38 1034 10325 1.335

T

0.128 0.130 0.1435 0.1625 0.172 0.195 0.225 0.256 O.jOl 0.332

0.1165 0.0724

+0.0322 -0.0087 -0.0528 -0.os90 -0.119 -0.1635 -0.165 -0.223 -9.221

set H

Fillets No.10 Nom1 Tail ti = -1 Flaps at 38" Elevutors at 0'

P= 14.8 btim v = 64.2 m s 0

Z’ . +I .7

4-2 6.65 9.2

11.7 12.95 -l4i3 15.6 16.85 18.15 19.45 20.75

g :;

cr./ 0.273 0.106 0.511 0.110 0.741 0.1215 0.973 o-135 1.195 O-157 1.43 0.184 1.56 0.240 1.595 0.271 1.545 0.318 1.505 0.347 1.63 0.361 1 LO 0.410 1.52 WA8 1.60 3.497 1.515 0.547 1.455 0.590

I -i- 0.0812 0.0423

+o.o053 -0.0342 -O*O733 -0.1205 -0-2065 -0.2115 -0.276 -0.277 -0.284 -O&279 -0.2135 -0.283 -0 274 -&265.

P = 23.6 HJIIOS pv2 = 216 lb./sg.ft. v = 64d FPS R = 3.72 x IO

a

-3.25 -0.75 +I.75

k;5

9125 11.8 IL.23 16.83 18.15 lY-45 20.75 22.03

1 0.297 0.537 0.762 0.981 1.22‘ 1.435 l-F7 I.555 1.625 l-665 1.6aaF; I.& I.575

0.105 0.112 0.123 0.139 0.160 3.181 0.238

.320 0.375 OS405 3.G 0.485 O&l

0.0720 ~I.0321 -0.0078 -O&435 -0.0848 -0.124 -0.205 ,

-0.277 G -0.287 I -0.292 -0.256 -0.293 -0.295

GL ,,I.69 at 19O

Set H (C&L)/

P = 24.2 Atnos pV2 = V = 82.:'FPS

366 lb./spft. R = 4.92 x 13

n -T-

Z’ 4. +I .eg

Z' 9:3

11.8 13.05 14.3 15,6 16.9 18.2 19.5 20.75 22.1 23.4

0.0810 +C.v378 &.ti163 ,a, 5,‘9 -s.c917 -0.1275 -0,202 -0.274 -0.280 -0.283 -0.291 -03292 -0.298 -0.305 -0.288 -0.282

- 16 -

Set H (Contd.)

-

CL ~* 1.71 at 21°

set s/

set J

p =I.0 xtlnos pv* = 13.3 : v = 75 PPS R = 0.201

a I cr -1 .y -0.051 0.0386 -0.0163 -0.65 +0.069 0,0389 -0 .a&60 ~I.65 0.180 0.0408 -0.0702

3.15 0.4.06 0 .a41 -0.1157 5.6 0.648 0.0533 -0.1635 8.1 0.881 0.0690 -0.217

10.65 1.03 0.0991 -0,291 II.85 1.085 0.120 -0.297 13.15 1.095 0.150 -0.295 14A5 I.09 0;1a2 -0.313 15.75 IelO 0.209 -0.311 17.1 1.015 0.272 -0.328

Lb./s A%. x 10 %

CLmx 1.1 at 13"

Fillets No.10 Xornal Tail qt = +2 Flaps at O" Elevators z.t 0'

lb./s "3-t. x IO %

P = 3.2 ab0s gr2 = 29.5 v = 6; !.9 FPS R = 0.533

a 1 cL I I %I

-3.15 -1.85 -0.6 +0.65

3.15 5.65 8.1

10.5 11.85 13.05 14.45 15.65 16.95 18.3

-0.194 0.0271 +0.0144 -0.078 0.0259 -0.0136 +0.045 0.0246 -0.0429

0.159 0.0250 -0.0671 0.406 0.0310 -0.118 0.652 0.0398 -0.1665 0.882 0.0597 -0.222 1.08 0.0859 -0,282 1.12 0.106 -0.311 1 .I1 0.135 -0.306 1.135 0.164 -0.312 1.15 0.201 -0.323 1.115 0.259 -0.345 1.035 0.299 -0.34-2

-

( :Lmx 1.15 at 159

P= 14. v=63.

-3.25 -1 .Y -0.6 3 +0.6

::i 8.05

lOA 12.95 14.25 15.55 16.8 18.1 19.35 20.65 22.0

I ZLL. 1.41 at 2o"

85hmos pV2~137.8 lb+ft. ,5 FPS R =*A4 x 10 .-

--I- T %i C L --

-0.l93 -0.063 +o.w

0.165 0.412

so.667 0.899 1.135 1.225 1.24 1.295 1.335 1.38 I.405 1.395 1.35

CD -- 0.0241 0.020: 0.0192 0.0193 0.0251 0.0371 0.0556 0.0821 0.1255 0.161 0.185 0.214 0.243 0.264 0.313 0.375

+0.0026 -0.0256 -0.0498 -0.0734 -0.4225 -0.173 -0.222 -0.282 I -0.324 s -0.344 , r.359 -0.376 -0.393 -0.400 -0i410 -0.422

Set J (Cod&)/

Set J (Co&L)

P = 22.4 btrms v = 65.5 ms

pV2 = 216 lb./sz.ft. R = 3.65 x IC

a

-3.2 -1.9 -0.65 4.6

:::5 8.05

IO.55 13.05 15.6 18.15 19.4 20.7 22.05 23.35

-0.192 -0.073 +0.050

0.167 0.415 0.666 0297 1.115 1.24 1.31 1.415 I.45 1.45 1.415 1.39

- c i

-

- 1 %i

0.0232 -0.0023 0.0207 -0.0234 0.0201 -0.0505 O-C204 -0.0749 0.0257 -0.1215 0.0374 -0.1693 0.0536 -0.215 0.0806 -0.271 0.1245 -0.320 0.184 -0.364 0.236 -0.407 0.266 -0.430 0.309 -0.429 0.352 -0.430 0.400 -0.456

CL-l.45 at 2o"

P = 24.0 Ahos pV2 = 366 lb./sa.fr;. V = 82.3 PFS R = 4.9 x 106.

a

-3.25 -1.95 -0.6 +0.65

;:: e.05

10.45 12.9 15.5 16.75 18.0 19.25 20.55 21.95 23.3

-

-

-

c, -0.200 0.0234 +o.cc57 -0.078 0.0205 -0.0;95 +O.O45 0.0198 -0.0444

0.163 0.0202 -0.0682 0.41 5 0.0259 -0.1182 0.658 0.0377 -0.163 0.894 0.0560 -0.211 1.107 0.0791 -0.263 1.255 0.124 -0.318 1.315 0.184 -0.37O 1.39 0.209 -0.396 1.43 0.238 -0.408 1.465 0.269 -0.432 1.49 0.304 -3.442 1 A4 0.360 -0.455 1.37 0.401 ' -0.454

CL mx 1.42 at a0

Qd

--

i

Q

I

set lg

P = 1.0 Atms ,,V' = $3.3 lb./sq.ft v = 75.5 FPS a = a.za x 106

P = 3.31 LtT-03 v = 62.C FE

pV2 = 29.55 lb& R = 0.534 x IC 6

.ftt. P = 14.9 htmos pV2 = 137.5x+ v r 63.4 z?Fs R = 2.34 x IG t

cit.

a

L3.2 -0.155 a ic399 a.c23a -1 .v -0.643 0.0336 -0.0487 -0.65 +c.c63 a .ojvv -0.~688 +0.65 6.174 O.C412 -0.d836

3.15 3.403 0.0461 -e.130 5.6 0,636 O&544 -0.168 a.1 cd.886 0.0706 -0.255

IO.65 1 .c47 0,?017 -0.339 Al.85 129 0.123 -0.346 13.15 1 .I1 0.149 -3.344 14.45 1 d-95 ti.lau' a.362 15.75 1 .I1 0.207 -0.366 17.1 1 .c2 0.267 -0.3sc

cL

cr, mx 1.11 at 13O

set K

Frllets 1;0.10 Nomal Tail 7-t = -I Flaps at O" Elevators at +10°

a

-3.25 -1.95 -0.7 +0.6

3.1 z-25

,3:55 11A5 13.1 14.4 15.7 17.3 18.3

-0.165 C.6314 -C.OG35 -0.051 0.0285 i-O.065

-0 -0923 C.C279 -0.1195

0.186 0.0279 4.146 0.432 0.0345 4.197 0.675 iis -ccl46 OS3 GA652 -0.3b3 3.095 0.~926 -0.355 I.145 0.~063 -0.359 1 .-i2 6.136 -0.357 1 iI4 C*-i62 -0.361 1.15 0.196 A.369 I*135 0.255 -0.401 1.08 0.300 -Z&JP

cL- 1.15 at 16' (possibly 12')

a

-3.3 -2.0 -0.65 d.6

:::, 8.05

lC.55 13.05 15.6 16.85 Is.15 19.45 a.75 22.05 23.35

T 1, I

I I

-

cL

42.177 C .C253 -0L479 -0 -060 0.0229 -0.3723 +Z.C59 O.S21'e -C.C963

G.172 C.C22d d.117 d.4CV c, .0283 -3.16c5 0.653 0.0403 -0.225 0.884 c-0563 -0.2@ 1.085 0.0847 -0.295 1.21 C.127 -0.3JU 1.28 L-189 -a .4G 1.33 c.215 ;.4s 1.385 0.245 -2 -459 1.41 0.277 -a .466 1.39 2.314 -0.473 4.375 0.35s -3 J&9 1.35 0.398 A.524

CL nax 1.41 et 19.5O

--

Set K (Cm%)/

set K (centa.)

P = 23.75 Atms pV2 = 216-G lb./sq.ft. v = 64.2 FEZ R = 3.665 x lo5

a

-3.3 -2.c a.55

3.05 5.55 a.05

10.55 13.0 45.6 16.85

:z5 20.7 22.0 23.3

-c-.184 -c.c58 0.179 0.421 0.673 0.894 1 .I06 Is23 1.30 1.375 1.41 I.465 1.45 1.44 1.40

c.2256 a.G243 0.0235 0.0295 0.0418 0.0595 0.0843 0.128 0.185 0.211 0.237 0.267 0.306 Q.348 0,396

-2.C556 -b.fb823 -G.127 -0.172 -0.220 -0.260 a.jQ6 -0.362 -O.&l2 -0.4-44 -0.L66 -O&30 -0.491 -o-510 AI.528

I = 24.9 Ltrms $I2 = 365.5 lb./sq.ft. v = 83.2 E'S R = 4.95 x IO6

-3.35 -1.95 -G.75 co.55

K? & 12.45 13.; 15.5 16.8 18.1 19.35 2C.6 21 .9 23.2

-(:.I84 -c&3 +~.c66 G-175 0.4?7 0.661

x:2 . p 1.215 1.33 I.35 1.43 1.47 1.515. 1.45 1.4c5

GJJ229 c.c:ziy O.?2Cl d.0215 C.C280 0.0401 G.G579 0.0818 c.1535 0.187 0.214 C.239 0.269 3.3G4 0.35c. 0 .L+oo

y44~ .

-0.c951 x.1155 -c.l603 -3.2~4 -0.29> -C'.295 -6.371 -?'A27 X.458

Ivt-g~ 1 -0:512 -3.512 -c.54G

I

c, nax 1.52 nt 21~

Set L/

---- I) = l.G n+xns pv2 = 13.32 lb./‘sq.ft. v = 75b8 FEi R = 0.298 x ~6

P = 3.25 i,kms ,0”2 = 23.5 lb.jsE.ft. v = 63.C 3iJs R = 0.527 x Iv

p = 14.9 ~~ti:os pv2 = 137.8 lo./+t. V = 63.7 "is El = 1.42 x 4

a %l a a % cL

-3.15 -2.287 ah-457 0,391 -I .a5 %.I73 o.a+49 c.368 -0.6 -0.056 0.0435 C.jl4 +G.7 +G.iC3 osw3 0.309

3.2 0.305 c&43 2.232 5.65 0.551 1:.01+86 .:.I72 8.15 c.791 C*,C606 i.129

lZr65 5.949 Lm .ca46 C&598 11.9 1 .a 0.102 @.C348 13.2 IL35 2.135 O.C~071 54.5 ?.a5 k.164 -0.L.289 15.8 IL35 2.191 -3 .! 5i“a 17.1 c.945 0.250 -t?.C674

-3.2 -1 .Y -0.6

+3.7 5.6 8.f

10.6 Il.85 13.15 14.45 15.7 17.05

-5.295 A.?85 4 261 +&33

0.539 0.772 0.967 1.027 1.02 1.045 1.075 1.04

:'.'->3y3 a.355 0.0365 ! 0.744

-3.15 -1.85 -0.6 +3.7

9: 8:2

qc.7 13.2 15.7 16.3 -1V.F5 21 .35 22.65

4.269 -0.151 4.037 +0.385

0 -222 0.562 3.774 0.796 1 .$?4

5.C j24 0 a296 c.1;2:7 0.0265 0.9299 G-6376 C&J533 z.0749 c.112

G.325 0.336 0.268 0.269 0.24s

a.0324 ! 0.351 0 .r:joz ’ 0.338 0.0386 1 0.218 o.oj54 0.0767 0.0954 0.?245 0.1515 0.186 0.244

0.153 0.105 0.065 0.0074

-0 23258 -0.0605 -0.w45

0.219 2.176

I

C.1265 2 o.ziP7 I

cL ,-3X I .32 3t 20’

set L (c&d.)/

- 22 -

Set L (Contd.)

P = 24.05 I.tr.us pV2 q 216.5 lh.jsq.ft. Vz63.0 FPS ii = 3.02 x 106

a

-3.1 -1 .a -0.55 io.75

3-25 5.7 0.25

10,75 13.25

::*‘o: 18:3 19.7 20.85 22.45 23.5

co -0.267 0.0336 a.315 -0.147 0.0287 0.303 -0.0283 0.0261 0.281 4J.091 0.0247 0.261

0.331 0.0288 0.220 0,570 0.0388 0.185 0.800 0.0512 0.147 1 ,Ol 0.0750 0.101 1 .I7 0.116 0.0143 1.21 0.174 -060659 11275 0.199 -0.0914 I+? 0.230 -0.119 Ii355 0.255 -0,139 1.355 0.290 -0.158 I.325 0.331 -0.779 1.275 0.375 -0,199

CL L,aX 1136 at 2o"

set If

Fillets I:o.lC Nod Tail nt = -lo Elevatom at -lc"

-.-

a -.

-3 “4 -z .75 +I .75

2 8”3 9 25

1 I. .45 11.65 12.3 14.2 15.6 16.9

T -T-

I / I

j. 8 .

T

cL

0.194 0.432 "A54 L1.869 1 La5 I.785 1.275 1.3-, I.30 1.34 3.36 1.14 1.18

c.115 3.122 3.127 0.140 L.357 0.166 3 .I %j L.222 0.254 L.2Y2

%i --

'c.252 3.219 c7.2?2 3.191 0.171 c.155 c.123 s.237

-:.0225 ->.I>5

0.114 0.117 3.125 ,:.I43 G.'i59 k; .: 61 d.231 Ca2',6 C.3~I2 i‘ D j& C.364 o.lp.2 3J+31 ~"482 :, -53.:

a

-3.2 d.65 +I.%5

4.35 6.85 9.35

11.7 12.95 14.25 15.55 16.%5 18.1

cL a / CL

-3.3 c.236

i- T

12.95 / 1.53 14.2 / 1.52 15a5 16.85

j 1.53 i i.57

18.15 j 1.58 19.45 / 1.62 2c .s / I.555 22.1 j 1.5:

I

2.269 2.224 C.168 z.: 48 2.119

+'L ."91 -boil9

: '2' I. " G,.175 W.lY-

a

-3.35. A.75 +I r75:

i-G5 . B.Ojys 9.25

IL.551 II*8 13.1 14-4 15.7

2.24: P.472 0.7c4 CG941 I.17 1.395 1.5G5 I -48 l..L85 1.5L5 I.565 1.61 : .63 1.61 I.525

?.I19 2.234 01125 3.135

I 0.2L2 0.234

5.142 C&217 a*1 60 c.477 &I$$2 2.133 2.195 0,239 c.233 +s"G 7 2.253 -a.'346 ~a6 -3.:16

-3.136 / 4.1%

f.112 cut115 c.124 2.'141 :.I59 ':. ‘ i 91 c.24E G.238

2.276 3.23: T.191

-3.147 2.111

+- S68 -; .Sj6

j -0alC8 , 3.317 1 -:.155 G-348 j -,.<65 c c.374 j -0.195 ' LAG; / -2.259

/ -2.216 L.487 I x.224 v.54% i 4.242

I

CL- ii3 at 12O c, max 1.36 at 14'

Fillets X0.8 Flaps at O"

set N

>To Tail.

-4*9 -2.35 +0.25

2.75 5.25 7 8 9.05

lb.3 11.5 12.75 14.05

:.E5 40

-0,255 ObO37Y -0.0877 -0.058 01030; -0.0645 +0.147 0.0305 -0.0464 O-352 0.0344 -0*0292 0,570 0.0419 -0.0087 O-776 0.0518 co.0173 0.852 0.0633 0.0285 0.899 0.0746 0.0466 0.757 0.0897 0.0570 O.Y59 0.117 0.0532 0.960 0,154 0.0379 O.Y55 0.180 0.0408 0.910 0.235 0.0245 0.8-W Ob274 0.0115

P = la0 Atmos pV2 = 13.22 lb./s %

.X-t v = 7k.7 FPS R = 0.20 x 10

CL - 0.96 at 12O

-4.95 -0.285 0.0293 -0.0854 -2.3.5 -0.068 0.0215 -0.0686 +0.2 +0.147 0.0212 -0.0494

2.7 0.367 0.0256 -0.0306 5.2 0.587 0.0346 -0.0118 7.75 0.796 0.0494 +0.0083 Y.0 0.882 0.0593 0.0207

10.2 O.Y68 0.0706 0.0297 II.45 1 .COl 0.0859 OiOl+66 12.7 1.008 0,307 0.0595 14.0 1.014 0.148 0.036 15.3 1.030 0.180 0.0309 16.6 1.006 0.229 0.0180 17.95 0.961 0.270 0.0050 19.3 0.732 0.304 -0.0015

P = 3.15 Atmos v = 62.7 FPS

pV2 = 27.2 lb./s R = 0.518 x IO %

.ft.

--

p s 4.44 Atmx v = 6886 FPS

pV2 = 49.Olb./s3 f't. R = O.Ei36 x 10 5

a

-4s95 -2.35 to.2

2.7

:::5 7.0

10.2 11.45 12.65 13.95 15.25 16.55 17.95 19.25 20.6 21.7

% ---

--

%

-0.289 0,023.L -0.076 0.0199 +o.-lL.5 0.0185

0.369 0.021L 0.597 0.0323 0.795 0.0473 0.893 G.0581 0.977 0.0691 I.012 0.0837 1.096 0.0391 i .c75 0.135 I .088 0.170 I ,088 0.210 I.017 0.268 0.962 0.300 O.yi8 0.339 0,890 0.366

T -0,0803 -OS0773 -0.048s a.0273 -0.0104 i-o.0123

0.0102 0.0270 0.0376 ' o.o.!Lyo F 0.0447 t 0.0380 0.0320 0.0104 o.o:oy 0.0050 0.0030

Set N (C&d.)/

set N (corlta.)

P = 13.6 A+ZIOS v = 65.6 FPS

,,V2 = 135.7 lb./sq.fi. R = 2.22 x 106

P = 21 .a ktm0s p2 = 230 lb./sq.ft. V= 68.6FPS R = 3.7 x go6

a / c-L --

-4.9 -o.jc& 0.0239 -0.0861 -2.35 -o.caj 0.0169 -0.0654 + .2 co.144 0.0162 -0.0473

2.7 Ci370 0.0202 -0.0265 5.25 0.6C8 CiC306 -cj,c!o62 7*a 0.844 0.0492 co.0228 9.G 0.942 OS593 +@.0254

10.25 IL24 GA713 G110331 11.4 1.116 0.0851 0.0390 12.7 1.18~ 0.1037 0.0465 14.0 I.185 Grlj7 0.0410 15.3 1.17 J.175 0.032 16.55 1.225 G.2CG 2.024 17.9 1.26 0.23~‘ 0.0335 19.2 1.26 c.262 Q.0295 Tu.5 . 1.255 ~*299 0 A23 21.8 1.23 0.34& 0.006 24.45 1 .I3 C.432 a.015

-i-

cL mx 1.26 at 18' CL mx 1.31 at Iv&"

%! a --

-4.85 -2.3 d.2

2.75

::8’ 9.1

10.35 11.55 12.8 14.1 15.4 16.65 18iG IV.35 20.6 21.9 23.2 24.58

c, co i -0.307 0.0246 -0.079 0i0191 +0.145 0.0172

0.366 0.02~8 0.627 @.@349 0.839 0.0492 0,946 0.0520 1.025 0.0696 1.110 0 da27 1.165 0.157 1 il4 0.151 q .4a5 0,173 lr23 0.198 1.27 0.222 I.305 0.241 1.28 c.292 1.25 oi336 1~215 0.375 ii18 0.4li

- %I

-0.0853 -0.0693 -0.0472 3.0256 -G.c051 +G.C167

0.0213 CiG375 0.0464 0 dud3 C .C295 0.0338 C.0368 0 .L3a7 G&367 od232 O&l27 0.0038

-C*OG17

Set P/

P = 1.0 ktcios pV2 = 13.3 lb./s .ft. v = 76.3 FPS R = 0.194 x 10 %

a

-3.4 0.366 0.107 -0.248 -0.85 0.572 0.118 -0.231 +I.7 0.781 0.130 -0.214

4.2 0.994 0.142 -0.1885 6.65 1.205 0.1620 -0.172 9.2 1.345 0.202 -0.1475

IO.5 1.375 0.239 -0.155 11.75 1.37 0.265 -0.1405 13.05 1.335 0.309 -0.1555 14.35 1.34 0.338 -0.1495 15.65 I .34 0.374 -0.1605

cr, %I

set P

Fillets No.10 No Tall Raps at 380

P = 3.26 Atmos v = 63.2 FPS

a

-3.45 -0.9 -1.65

i-k5 9:15 :I.7 13.0 14.3 15.6 16.95 !a.25

- 1

~

0.372 0.582 0.813 1.02 1.23 I.385 1.40 1.375 1.375 1.37 1.31 1.23

i

0.102 0.108 0.1215 0.135 0.156 0.1yr 0.258 0.304. 0.333 0.3a2 0.445 0.497

I- -L.. I 1

I-

Qf ) a -0.257 -3.4 -0.240 / -0.9 -0.227 +i .55 -0.207 4.15 -0.1880 6.65 -0.960 9.15 -0.1485 11.7 -0.1565 14.3 -0.154 15.6 -0.170 16.9 -0.185 18.15 -0.1875 49.45

20.8

II 22.1

O.jEl 0.600 0.816 1.025 1.225 r.445 1.56 1.51 1.53 1.55 1.58 1.58 1.55 1.48

0.102 0.1oy 0.122 0.138 0.160 0.185 0.239 0.317 0.344 0.376 0.411 0.445 0.495 0.5j8

-0.263 -0.246 -0.230 -0.211 -0.189 I -0.173 -0.1705 ix -0.168 I

-0.1635 -0.1645 -0.166 -0.161 -0.172 -0.179

CLmx 1.42 at II0 CL nax 1.58 at 19O

Set P (Co&d.)/

. - ser; P (conta.)

P = 24.3 Atolos PV' = 216 lb./s2 .ft . 7 = 63.5 FPS R = 3.7; jY I"

a

-3.5 -3.95 +I .6

4.2 6.65 9.2

11.75 1L.35 16.9 18.2 19.5 22.6 22.15

cr

C.381 C.6L'C 3.018 I .(I28 1.245 1.455 1.555 1.52 1.59 :.tj -1.65 1.6:5 1.515

- 1 I -CD : % - 5.101 j a.264 C.lC85 0.121 G.139 0.156 3.185 0.243 0.319 2.375 C&5 0.438 lY..49S c.544

cLmax 1.65 at 19'

-L~.248 -~: .229 42.211 -c.192 -C.176 -'l.l84 -0.273 4.163 4.157 -.!.162 -3.175 -Lb.185

P = 24.75 ktmos $I2 = 3651b&qft. Vz82.9 PPS R = 4.67 x 1~6

a / CL - -3.35 -0.95 61.6

:-: . 9.25

11.75 14.3 17.0 16.3 19.6 2C.85

05376 ' ;.kg

. 1 .035 1.255 1.475 I.58 I i53 I+60 1.63 I.645 1.61

22.2 j 1.4E

I 7 I

-i- I I

cl+i I

/

cn

3.1Lil G.?r;8 C.$22 0.1375 C*l585 O.lVTi a.253 c..jlC 0.363 c.418 0 .45G 11.5c?5 c.555 I

T

-0.263 -c.246 -G.232 -0.211 -0 .I 91 -0.174 -0.177 -:,*I71 3.169 -c-,.174 -8j.171 -\.I88 -0,193

- 28 -

Appcnduc I --.-

Comparison of C.A.T. Tests vith Prcliininlrrs Flight Tcstt.

CL mx (Flaps rind und,crcarriago up)

w. (No Propollors)

l.46 at R = 5 x lo6 (still rising) (Curve F, Fig.5)

Flight (~~indmi.lling Propullcrs)

l.U+ at R = 9 x 106

CL max (38' Flaps)

C.A.T. including centre flap) No Propollors)

Plight less centre flap) t Winduilling PropollurLi)

1.705 at R = 5 x 106 (still rising) (Curve H, Fig.5)

1.76 at R = 9 x lo6

Ncutrnl Point (Flaps mnd undarcuring~ up)

C.A.T.

0.42 from R = 0.2 x lo6 to 5 x lo6 (No Propellers)

Fluqht

Lxs 0.025: roughly (T~indmlling Propcllcrs)

i.c. 0.395; 0.396 up to R = 25 x l& (Vinduilling Propcllors)

In the course: of tunnel tests, with propellws fitted, the blnd;ts wax d.u,mg,sd and the results wrc not considered to be reliable. It is intcrosting, howvur, that the cstiinate of the effect of propollors on h, (md,ds by Messrs. k-nlstrong Whitnorth from tho C.A.T. ixeosurcmcnts and not by oursdvcs) brings th2 value into close agreownt with the flight test result.

Appendix II/

Ordinate No.

---------_m_*.

1 ~

:

4

2

i

9 10 11

:: 14 15 16

z 19 20 21 22 23 a.

- 29 -

kppcndix II

S&Am ordimtos at B J. (Fig.1)

True chord 6.04" L.X. mdius O.Oyy" T.E. roanls 0.~08"

,___________-___-_-_--_______-_----_----_----C---_---_--5-- Distance frolfi L.3. I Ordinntcs (inches)

.-,--------,-,_,,------,,---------,----------------------------- Inches ; Przction of ! Top Bottom

chord f surfaoo I Surf ace

0.030 0.045 0.075 0.151 0.302 0.453 0.604 0.906 1.208 1.510 1.812 2.ll4 2.416 2.718 3.020 3.322

::",2 4.228

0.0125 0.025 0.05b 0.075 0.100 0.50 0.20 0.25 0.30 0.35 0.40 0.45 0.50 0.55 0.60 0.65 0.70 O.j!i 0.80 0.85 0.90 0.95

i 0.082 0.101 0.133 0.191 0.276 0.341 0.395 C.481 0.548 0.600

Z~ $0;

0;660 0.621 1.564 0.438 0.425 0.348 0.270 0.194 0.122 a.057

0.069 0.084 0.106 o.l.45 0.196 0.234 0.263 0.310 '1.345 0.371 0.391 0.404 A.410 0.4% 0.397 0.370 0.333 0.291 0.246 0.199 0.152 0.107 0.066 0.030

- - - - - - - - - - - - - - - - - - -_--- -_--- - - - - -c--- - - - - - -

12 823 Gj- I .

i i i

I 1 i

I I :

! I

12,a23 FIG 2

.

32’ Flaps - orlglnal --- mod,fw.d

l

+; !‘“’ ,. , -.. .- +

\ \ ‘3 \

\ \ 0

‘. ‘\\ I -4 z9’-- 0.5. -

J f

7 0 5

Flap and Fnze Seetmns at B J (Fig I)

a 200

AWpollo . Type4 CL Cut-we.

12,823 i?G 5

AW Apollo Mawmum L6t Curves

12,823 FIG 6

I R\ I U I I \ I

/ A~pollo Fkchmg Moment CceFk~ents

0 0’

A

00

00

=Q”

00.

00

00

OC

OC

0,

08 6672411/207t3 K3 1151 CL

C.P. No. 40 12,823

A.R.C Technical Report

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